The invention provides a
satellite configuration suitable for configuring a large-aperture optical camera and needing on-
orbit rapid maneuvering. The
satellite configuration comprises a
service module, a load module, a camera light shield, a two-module
locking mechanism and a
solar cell array. The
service module adopts an outer hexagonal and inner hollow structure, and the outer hexagon fully utilizes the available envelope of the carrying fairing to provide a larger installation space for the whole
satellite, so that the height of the
service module is reduced, and the overall
center of mass of the satellite is reduced; the inner circular hollow part provides an installation space for the camera
secondary mirror support cylinder and the camera light shield. The load cabin is located below the service cabin when the satellite is vertically parked, and the camera
secondary mirror supporting cylinder penetrates through the service cabin and provides an installation interface for the carrying separation device. The two-cabin
locking mechanism provides mechanical support for the service cabin. The
solar cell arrays are symmetrically arranged on the two sides of the service module. The problem that the
inertia of the whole satellite is too large is solved, the requirement for in-
orbit rapid maneuvering of the large-aperture optical satellite is met, and the method has the
advantage that the mechanical environment and the space thermal environment of the load active section are improved.